针对旋转稳定火箭弹提高射程和增大飞行速度带来的飞行不稳定问题,进行了基于稳定飞行的转速设计,并利用FLUENT软件和用户自定义函数UDF,在旋转壁面边界条件下对火箭弹进行气动特性仿真,分析了火箭弹阻力系数、升力系数和马格努斯效应随攻角的变化规律。结果表明:在设计转速为2827.43rad/s下,气动仿真和外弹道仿真结果能够满足火箭弹飞行稳定性要求,从而为火箭弹增程设计提供了依据。

In view of the problem of flight instability brought by increasing range and speed of spin-stabilized rocket, the rotation rate based on steady flight was designed. The aerodynamic characteristics were simulated under the condition of rotating body surface by FLUENT and UDF. The trend of drag coefficient, lift coefficient and Magnus force with the variety of attack angle was analyzed. The results show that the aerodynamic simulation and exterior ballistics simulation results could meet the requirement of flight stability when the design speed is 2827.43rad/s. Eventually, It can provide some references for rocket design of increasing range.